# TCDS A-763: Lockheed Martin Aeronautics Company - Type: Type certificate data sheet - Status: Current - Holder: Lockheed Martin Aeronautics Company - Revision: 19 - Revised: July 23, 2012 - Product: Aircraft, Large Airplane - Certification basis: CAR 4b - Registered aircraft: 2, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/b6/8f/b68fb81ef754ae512cad0d25743dda53d012c6f693e8c030d1c177dc8135d794 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/BAA5A3277242431386257A45004A6DF8.0001 - Page: https://openairdocs.org/tcds/A-763 ## Models (6) As the data sheet lists them. - 149-46 - 649-79 - 749A-79 - 749-79 ((C-121A, VC-121B)) - 649A-79 - 49-46 ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 Rev. No. 19 18 18 18 14 16 18 18 18 18 14 18 18 14 18 18 10 10 16 18 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A-763 Revision 19 LOCKHEED 49-46 149-46 649-79 649A-79 749-79 (C-121A, VC-121B) 749A-79 July 23, 2012 AIRCRAFT SPECIFICATION NO. A-763 This data sheet which is part of Type Certificate No. A-763 prescribes conditions and limitations under which the product for which the type certificate was issued meets the airworthiness requirements of the Civil Air Regulations. Type Certificate Holder Lockheed Martin Aeronautics Company 86 South Cobb Drive Marietta, GA 30063 Type Certificate Holder Record Lockheed Aircraft Corporation Burbank, California I - Model 49-46, Approved October 14, 1946 (See NOTE 14 for interrelationship of models) Engines 4 Wright Cyclones 745C18BA- 3 with 16:7 reduction gear ratio. Fuel AN grade 100/130. Engine limits Low impeller ratio 6.46:1 Maximum continuous: (Sea level) 43.5 in.hg., 2400 rpm (2000 hp) (Straight line manifold pressure variation with altitude to 4800 ft.) 41.5 in. hg., 2400 rpm (2000 hp) Take-off (two minutes): (Sea level) 46.0 in.hg., 2800 rpm (2200 hp) (Straight line manifold pressure variation with altitude to 6300 ft.) 44.0 in.hg., 2800 rpm (2200 hp). High impeller ratio 8.67:1 Maximum continuous: (8000 ft.) 43.0 in.hg., 2400 rpm (1800 hp) (Straight line manifold pressure varia tion with altitude to 15000 ft.) 40.0 in.hg., 2400 rpm (1800 hp). Take-off (two minutes): (10,600 ft.) 44.0 in.hg., 2600 rpm (1900 hp) (Straight line manifold pressure variation with altitude to 16200 ft.) 42.0 in.hg., 2600 rpm (1900 hp). Airspeed limits Level fli ght or climb - 271 mph (236 knots) for sea level to 16000 ft. Above 16000 ft. reduce speed 5 mph (4 knots) for each additional 1000 ft. of altitude. Flaps extended (Landing position) 146 mph (127 knots) (Approach position) 146 mph (127 knots) (Take-off position) 200 mph (174 knots) Landing gear extended or during gear operation - 175 mph (152 knots) Glide or dive Without Speedpak and/or deicer boot s installed - 324 mph* (282 knots) for sea level to 13000 ft. Above 13000 ft. reduce speed 6 mph (5 knots) for each additional 1000 ft. of altitude. (*Note: When airspeed instrument (0-305 mph) is installed, the above-noted glide or dive speed should read 305 mph instead of 324 mph and the corresponding altitude should read 16000 ft. instead of 13000 ft.) A-763 2 With Speedpak and/or deicer boots inst alled - 300 mph (261 knots) for sea level to 17000 ft. Above 17000 ft. reduce speed 6 mph (5 knots) for each additional 1000 ft. of altitude. Usable ceilings See Approved Oper ating Manual (enroute climb curve). C.G. range See NOTE 1(b) for require d loading and gear retraction moment. Condition Weight Landing Fwd. Limit Aft. Limit lbs. gear sta. %MAC sta. %Mac Take-off 90,000 Down 535.7 20.3 556.4 32.0 77,800 Down 531.7 18.0 556.4 32.0 or less Landing 77,800 Down 531.7 18.0 556.4 32.0 or less Cruising 90,000 Up 531.1 17.7 556.4 32.0 Flight 77,800 Up 526.4 15.0 556.4 32.0 or less Weight limits Landing: 75,000 lbs. Take-off: 86,250 lbs. (Dump valves are required) 3-engine ferrying: 80,000 lbs. See NOTE 11 for other conditions applicable. See NOTE 7 regarding eligibility for higher weights. Minimum crew 3, Pilot and Copilot at +190 and Flight engineer at +226. Passengers Maximum 60 (CAR 4b.3812). See Appr oved Weight and Balance Report for actual number and location. Baggage See NOTE 4. Fuel capacity 2 inboard tanks (790 gal. ea.) 9,480 lbs. (+563). 2 inboard tanks (1,555 gal. ea.) 18,660 lbs. (+558). See NOTE 5 regarding "System Fuel and Oil". Oil capacity 2 inboard tanks (45 gal. ea.) 675 lbs. (+495) 2 outboard tanks (45 gal. ea.) 675 lbs. (+520). Control surface movements Main surfaces (booster pressure on) - Elevator 40° up 20° down Aileron 25° up 9° down Rudder 30° right 30° left Tabs (main surfaces in neutral) Elevator 22° up 22° down Aileron 12° up 12° down Rudder 25° right 25° left Flaps - 41° total angular travel. Serial Nos. eligible 1963 to 1965 inclusive, 1967 to 1971 inclusive, 1974 to 1980 inclusive, and 2021 to 2088 inclusive. Required equipment Items 1a or e; 101(a); 200(a), (b) or (c ); 201(a), (b), (c), (d), (e), (f) or (g); 202(a), (b), (c) or (d); 203(b) or (e); 205(a), (b), (c) or (d); 206(c) or (d); 508; 600; 601. II - Model 649-79, Approved March 14, 1947 (See NOTE 14 for interrelationship of models) Engines 4 Wright Cyclones 749 C18B D-1 with 16:7 reduction gear ratio. Fuel AN grade 100/130. Engine limits Low impeller ratio 6.46:1 Maximum continuous: (Sea level) 44.0 in.hg., 2400 rpm (2100 hp) (Straight line manifold pressure variation with altitude to 4400 ft.) 42.5 in. hg., 2400 rpm (2100 hp) Take-off (two minutes): (Sea level) 51.5 in.hg., 2800 rpm (2500 hp) (Straight line manifold pressure variation with altitude to 3100 ft.) 51.0 in.hg., 2800 rpm (2500 hp). 3 A-763 High impeller ratio 8.67:1 Maximum continuous: (9000 ft.) 42.5 in.hg., 2400 rpm (1800 hp) (Straight line manifold pressure variation with altitude to 16000 ft.) 41.0 in.hg., 2400 rpm (1800 hp). Take-off (two minutes): (10800 ft.) 44.0 in.hg., 2600 rpm (1900 hp) (Straight line manifold pressure variation with altitude to 15700 ft.) 43.5 in.hg., 2600 rpm (1900 hp). Airspeed limits Level fli ght or climb - 271 mph (236 knots) for sea level to 16000 ft. Above 16000 ft. reduce speed 5 mph (4 knots) for each additional 1000 ft. of altitude. Flaps extended (Landing position) 146 mph (127 knots) (Approach position) 146 mph (127 knots) (Take-off position) 200 mph (174 knots) Landing gear extended or during gear operation - 175 mph (152 knots) Glide or dive Without Speedpak and/or deicer boot s installed - 324 mph* (282 knots) for sea level to 13000 ft. Above 13000 ft. reduce speed 6 mph (5 knots) for each additional 1000 ft. of altitude. (*Note: When airspeed instrument (0- 305 mph) is installed, the above-noted glide or dive speed should read 305 mph instead of 324 mph and the corresponding altitude should read 16000 ft. instead of 13000 ft.) With Speedpak and/or deicer boots inst alled - 300 mph (261 knots) for sea level to 17000 ft. Above 17000 ft. reduce speed 6 mph (5 knots) for each additional 1000 ft. of altitude. Usable ceilings See Approved Oper ating Manual (enroute climb curve). C.G. range See NOTE 1(b) for required loading and gear retraction moment. Condition Weight Flap Landing Fwd. Limit Aft. Limit lbs. Position gear sta. %MAC sta. %Mac Take-off 94,000 Takeo ff Down 535.2 20.0 556.4 32.0 Climb or cruise 84,500 Ta keoff Down 531.7 18.0 556.4 32.0 or less Straight line variation between above listed values. Climb or cruise 94,000 Up Up 529.9 17.0 559.9 34.0 84,500 Up Up 526.4 15.0 559.9 34.0 or less Straight line variation between above listed values. Landing 84,500 Down Down 531.7 18.0 556.4 32.0 o r l e s s Weight limits Landing: 84,500 lbs. Take-off: 94,000 lbs. (Dump valves are required) 3-engine ferrying: 80,000 lbs. See NOTE 11 for other conditions applicable. Minimum crew 3, Pilot and Copilot at +190 and Flight engineer at +226. Passengers Maximum 60 (CAR 4b.3812). See Appr oved Weight and Balance Report for actual number and location. Baggage See NOTE 4. Fuel capacity Tanks 2 and 3 (inboa rd) (790 gal. ea.) 9,480 lbs. (+563). Tanks 1 and 4 (outboard) (1 ,555 gal. ea.) 18,660 lbs. (+558). See NOTE 5 regarding "System Fuel and Oil". Oil capacity With Item 1(b) or (f) propeller - 2 inboard tanks (56 gal. ea.) 840 lbs. (+455) 2 outboard tanks (56 gal. ea.) 840 lbs. (+474). A-763 4 With Item 1(d), (e) or (g) propeller - 2 inboard tanks (54 gal. ea.) 810 lbs. (+455). 2 outboard tanks (54 gal. ea.) 810 lbs. (+474). Control surface movements Main surfaces (booster pressure on) - Elevator 40° up 20° down Aileron 25° up 9° down Rudder 30° right 30° left Tabs (main surfaces in neutral) Elevator 22° up 22° down Aileron 12° up 12° down Rudder 25° right 25° left Flaps - 41° total angular travel. With Model 49 flaps installed in accordance with LAC Dwings 251010, 251011 and 273326, flap movement is reduced to 41 . Serial Nos. eligible 2501 and up Required equipment 1b, d, e, f or g; 101(b) or (c); 108(b); 200(b); 201(f) or (g); 202(a), (b), (c) or (d); 203(b) or (e); 205(b), (c) or (d); 206(c) or (d); 508; 600; 601. III - Model 749-79 (Army C-121A, VC-121B - See NOTE 16), Approved March 14, 1947 (See NOTE 14 for interrelationship of models) Engines 4 Wright Cyclones 749C18BD- 1 with 16:7 reduction gear ratio. Fuel AN grade 100/130. Engine limits Low impeller ratio 6.46:1 Maximum continuous: (Sea level) 44.0 in.hg., 2400 rpm (2100 hp) (Straight line manifold pressure vari ation with altitude to 4400 ft.) 42.5 in. hg., 2400 rpm (2100 hp) Take-off (two minutes): (Sea level) 51.5 in.hg., 2800 rpm (2500 hp) (Straight line manifold pressure vari ation with altitude to 3100 ft.) 51.0 in.hg., 2800 rpm (2500 hp). High impeller ratio 8.67:1 Maximum continuous: (9000 ft.) 42.5 in.hg., 2400 rpm (1800 hp) (Straight line manifold pressure vari ation with altitude to 16000 ft.) 41.0 in.hg., 2400 rpm (1800 hp). Take-off (two minutes): (10800 ft.) 44.0 in.hg., 2600 rpm (1900 hp) (Straight line manifold pressure vari ation with altitude to 15700 ft.) 43.5 in.hg., 2600 rpm (1900 hp). Airspeed limits Level fli ght or climb - 271 mph (236 knots) for sea level to 16000 ft. Above 16000 ft. reduce speed 5 mph (4 knots) for each additional 1000 ft. of altitude. Flaps extended (Landing position) 146 mph (127 knots) (Approach position) 146 mph (127 knots) (Take-off position) 200 mph (174 knots) Landing gear extended or during gear operation - 175 mph (152 knots) Glide or dive Without Speedpak and/or deicer boots installed - 324 mph* (282 knots) for sea level to 13000 ft. Above 13000 ft. reduce speed 6 mph (5 knots) for each additional 1000 ft. of altitude. (*Note: When airspeed instrument (0-305 mph) is installed, the above-noted glide or dive speed should r ead 305 mph instead of 324 mph and the corresponding altitude should read 16000 ft. instead of 13000 ft.) With Speedpak and/or deicer boots inst alled - 300 mph (261 knots) for sea level to 17000 ft. Above 17000 ft. reduce speed 6 mph (5 knots) for each additional 1000 ft. of altitude. Usable ceilings See Approved Oper ating Manual (enroute climb curve). C.G. range See NOTE 1(b) for require d loading and gear retraction moment. 5 A-763 Condition Weight Flap Landing Fwd. Limit Aft. Limit lbs. Position gear sta. %MAC sta. %Mac Take-off 102,000 Takeo ff Down 537.0 21.0 556.4 32.0 Climb or cruise 94,000 Takeoff Down 535.2 20.0 556.4 32.0 84,500 Takeoff Down 531.7 18.0 556.4 32.0 or less Straight line variation between above listed values. Climb or cruise 102,000 Up Up 532.6 18.5 559.9 34.0 94,000 Up Up 529.9 17.0 559.9 34.0 84,500 Up Up 526.4 15.0 559.9 34.0 or less Straight line variation between above listed values. Landing 84,500 Down Down 531.7 18.0 556.4 32.0 o r l e s s Weight limits Landing: 84,500 lbs. (See NOTE 17) Take-off: 102,000 lbs. (Dump valves are required) 3-engine ferrying: 80,000 lbs. S ee NOTE 11 for other conditions applicable. Minimum crew 3, Pilot and Copilot at +190 and Flight engineer at +226. Passengers Maximum 60 (CAR 4b.3812). See Appr oved Weight and Balance Report for actual number and location. Baggage See NOTE 4. Fuel capacity Tanks 2 and 3 (inboa rd) (790 gal. ea.) 9,480 lbs. (+563). Tanks 1 and 4 (middle) (1,555 gal. ea.) 18,660 lbs. (+558). Tanks 2a and 3a (outboard) (565 gal. ea.) 6,780 lbs. (+560). See NOTE 5 regarding "System Fuel and Oil". Oil capacity With Item 1(b) or (f) propeller - 2 inboard tanks (56 gal. ea.) 840 lbs. (+455) 2 outboard tanks (56 gal. ea.) 840 lbs. (+474). With Item 1(d), (e) or (g) propeller - 2 inboard tanks (54 gal. ea.) 810 lbs. (+455). 2 outboard tanks (54 gal. ea.) 810 lbs. (+474). Control surface movements Main surfaces (booster pressure on) - Elevator 40° up 20° down Aileron 25° up 9° down Rudder 30° right 30° left Tabs (main surfaces in neutral) Elevator 22° up 22° down Aileron 12° up 12° down Rudder 25° right 25° left Flaps - 45° total angular travel. With Model 49 flaps installed in accordance with LAC Drawings 251010, 251011 and 273326, flap movement is reduced to 41. Serial Nos. eligible 2501 and up Required equipment Items 1b, d, e, f or g; 101(d) or (e); 108(b); 200(b); 201(f) or (g); 202(a), (b), (c) or (d); 203(b) or (e); 205(b), (c) or (d); 206(c) or (d); 508; 600; 601. IV - Model 149-46, Approved March 18, 1948 (See NOTE 14 for interrelationship of models) Engines 4 Wright Cyclones 745C18BA- 3 with 16:7 reduction gear ratio. Fuel AN grade 100/130. A-763 6 Engine limits Low impeller ratio 6.46:1 Maximum continuous: (Sea level) 43.5 in.hg., 2400 rpm (2000 hp) (Straight line manifold pressure variation with altitude to 4800 ft.) 41.5 in. hg., 2400 rpm (2000 hp) Take-off (two minutes): (Sea level) 46.0 in.hg., 2800 rpm (2200 hp) (Straight line manifold pressure vari ation with altitude to 6300 ft.) 44.0 in.hg., 2800 rpm (2200 hp). High impeller ratio 8.67:1 Maximum continuous: (8000 ft.) 43.0 in.hg., 2400 rpm (1800 hp) (Straight line manifold pressure vari ation with altitude to 15000 ft.) 40.0 in.hg., 2400 rpm (1800 hp). Take-off (two minutes): (10,600 ft.) 44.0 in.hg., 2600 rpm (1900 hp) (Straight line manifold pressure vari ation with altitude to 16200 ft.) 42.0 in.hg., 2600 rpm (1900 hp). Airspeed limits Level fli ght or climb - 271 mph (236 knots) for sea level to 16000 ft. Above 16000 ft. reduce speed 5 mph (4 knots) for each additional 1000 ft. of altitude. Flaps extended (Landing position) 146 mph (127 knots) (Approach position) 146 mph (127 knots) (Take-off position) 200 mph (174 knots) Landing gear extended or during gear operation - 175 mph (152 knots) Glide or dive Without Speedpak and/or deicer boots inst alled - 324 mph* (282 knots) for sea level to 13000 ft. Above 13000 ft. reduce speed 6 mph (5 knots) for each additional 1000 ft. of altitude. (*Note: When airspeed instrument (0-305 mph) is installed, the above-noted glide or dive speed should read 305 mph instead of 324 mph and the corresponding altitude should read 16000 ft. instead of 13000 ft.) With Speedpak and/or deicer boots inst alled - 300 mph (261 knots) for sea level to 17000 ft. Above 17000 ft. reduce speed 6 mph (5 knots) for each additional 1000 ft. of altitude. Usable ceilings See Approved Oper ating Manual (enroute climb curve). C.G. Range See Note 1(b) for require d loading and gear retraction moment. Condition Weight Flap Landing Fwd. Limit Aft. Limit lbs. Position gear sta. %MAC sta. %Mac Take-off 100,000 Takeo ff Down 537.0 21.0 556.4 32.0 Climb or cruise 93,000 Takeoff Down 535.2 20.0 556.4 32.0 83,000 Takeoff Down 531.7 18.0 556.4 32.0 or less Straight line variation between above listed values. Climb or cruise 100,000 Up Up 532.6 18.5 559.9 34.0 93,000 Up Up 529.9 17.0 559.9 34.0 83,000 Up Up 526.4 15.0 559.9 34.0 or less Straight line variation between above listed values. Landing 83,000 Down Down 531.7 18.0 556.4 32.0 o r l e s s Weight limits Landing: 83,000 lbs. Takeoff: 100,000 lbs. (Dump valves are required) 3-engine ferrying: 80,000 lbs. See NOTE 11 for other conditions applicable. See NOTE 7 regarding eligibility for above weights. Minimum crew 3, Pilot and Copilot at +190 and Flight engineer at +226. 7 A-763 Passengers Maximum 60 (CAR 4b.3812). See Appr oved Weight and Balance Report for actual number and locations. Baggage See NOTE 4. Fuel capacity Tanks 2 and 3 (inboa rd) (790 gal. ea.) 9,480 lbs. (+563). Tanks 1 and 4 (middle) (1 ,555 gal. ea.) 18,660 lbs. (+558). Tanks 2a and 3a (outboard ) (565 gal.ea.) 6,780 lbs. (+560). See NOTE 5 regarding "System Fuel and Oil". Oil capacity 2 inboard tanks (45 gal. ea.) 675 lbs. (+495) 2 outboard tanks (45 gal. ea.) 675 lbs. (+520). Control surface movements Main surfaces (booster pressure on) - Elevator 40° up 20° down Aileron 25° up 9° down Rudder 30° right 30° left Tabs (main surfaces in neutral) Elevator 22° up 22° down Aileron 12° up 12° down Rudder 25° right 25° left Flaps - 41° total angular travel. Serial Nos. eligible 1963 to 1965 inclusive, 1967 to 1971 inclusive, 1974 to 1980 inclusive, and 2021 to 2088 inclusive. Required equipment Items 1a or e; 101(f); 200(b); 201 (f) or (g) (See NOTE 15); 202(a), (b), (c) or (d); 203(b) or (e); 205(b), (c) or (d); 206(c) or (d); 508; 600; 601. V - Model 749A-79, Approved February 15, 1949 (See NOTE 14 for interrelationship of models) Engines 4 Wright Cyclones 749 C18B D-1 with 16:7 reduction gear ratio. Fuel AN grade 100/130. Engine limits Low impeller ratio 6.46:1 Maximum continuous: (Sea level) 44.0 in.hg., 2400 rpm (2100 hp) (Straight line manifold pressure vari ation with altitude to 4400 ft.) 42.5 in. hg., 2400 rpm (2100 hp) Take-off (two minutes): (Sea level) 51.5 in.hg., 2800 rpm (2500 hp) (Straight line manifold pressure vari ation with altitude to 3100 ft.) 51.0 in.hg., 2800 rpm (2500 hp). High impeller ratio 8.67:1 Maximum continuous: (9000 ft.) 42.5 in.hg., 2400 rpm (1800 hp) (Straight line manifold pressure vari ation with altitude to 16000 ft.) 41.0 in.hg., 2400 rpm (1800 hp). Take-off (two minutes): (10800 ft.) 44.0 in.hg., 2600 rpm (1900 hp) (Straight line manifold pressure vari ation with altitude to 15700 ft.) 43.5 in.hg., 2600 rpm (1900 hp). Airspeed limits Level fli ght or climb - 271 mph (236 knots) for sea level to 16000 ft. Above 16000 ft. reduce speed 5 mph (4 knots) for each additional 1000 ft. of altitude. Flaps extended (Landing position) 146 mph (127 knots) (Approach position) 146 mph (127 knots) (Take-off position) 200 mph (174 knots) Landing gear extended or during gear operation - 175 mph (152 knots) Glide or dive Without Speedpak and/or deicer boots installed - 324 mph* (282 knots) for sea level to 13000 ft. Above 13000 ft. reduce speed 6 mph (5 knots) for each additional 1000 ft. of altitude. A-763 8 (*Note: When airspeed instrument (0- 305 mph) is installed, the above-noted glide or dive speed should read 305 m ph instead of 324 mph and the corresponding altitude should read 16000 ft. instead of 13000 ft.) With Speedpak and/or deicer boots inst alled - 300 mph (261 knots) for sea level to 17000 ft. Above 17000 ft. reduce speed 6 mph (5 knots) for each additional 1000 ft. of altitude. Usable ceilings See Approved Oper ating Manual (enroute climb curve). C.G. range See NOTE 1(b) for require d loading and gear retraction moment. Condition Weight Flap Landing Fwd. Limit Aft. Limit lbs. Position gear sta. %MAC sta. %Mac Take-off 107,000 Takeo ff Down 537.0 21.3 556.4 32.0 Climb or cruise 89,500 Takeoff Down 531.7 18.0 556.4 32.0 or less Straight line variation between above listed values. Climb or cruise 107,000 Up Up 533.5 19.0 559.9 34.0 89,500 Up Up 526.4 15.0 559.9 34.0 or less Straight line variation between above listed values. Landing 89,500 Down Down 531.7 18.0 556.4 32.0 o r l e s s Weight limits Landing: 89,500 lbs. Take-off: 107,000 lbs. (Dump valves are required) 3-engine ferrying: 80,000 lbs. See NOTE 11 for other conditions applicable. Minimum crew 3, Pilot and Copilot at +190 and Flight engineer at +226. Passengers Maximum 60 (CAR 4b.3812). See Appr oved Weight and Balance Report for actual number and location. Baggage See NOTE 4. Fuel capacity Tanks 2 and 3 (inboa rd) (790 gal. ea.) 9,480 lbs. (+563). Tanks 1 and 4 (middle) (1 ,555 gal. ea.) 18,660 lbs. (+558). Tanks 2a and 3a (outboard) (565 gal. ea.) 6,780 lb. (+560). See NOTE 5 regarding "System Fuel and Oil". Oil capacity With Item 1(b) or (f) propeller - 2 inboard tanks (56 gal. ea.) 840 lbs. (+455) 2 outboard tanks (56 gal. ea.) 840 lbs. (+474). With Item 1(d), (e) or (g) propeller - 2 inboard tanks (54 gal. ea.) 810 lbs. (+455). 2 outboard tanks (54 gal. ea.) 810 lbs. (+474). Control surface movements Main surfaces (booster pressure on) - Elevator 40° up 20° down Aileron 25° up 9° down Rudder 30° right 30° left Tabs (main surfaces in neutral) Elevator 22° up 12° down Aileron 12° up 12° down Rudder 25° right 25° left Flaps - 45° total angular travel. With Model 49 flaps installed in accordance with LAC Dwgs. 251010, 251011 and 273326, the flap movement is reduced to 41°. Serial Nos. eligible 2501 and up converted in acco rdance with Lockheed Service Bulletins 49/SB-500, - 500A and -545. Modifications covered by LAC 49/SB-500 were incorporated in serial Nos. 2589, 2590, 2601 and up, prior to delivery. Required equipment 1b, d, e (with 6801A-0 blades), f or g; 101(d); 108(b); 200(d) or (e); 201(f) or (g); 202(a), (b), (c) or (d); 203(e); 205(b), (c) or (d); 206(c) or (d); 209; 508; 600; 601. 9 A-763 VI - Model 649A-79, Approved December 20, 1949 (See NOTE 14 for interrelationship of models) Engines 4 Wright Cyclones 749 C18B D-1 with 16:7 reduction gear ratio. Fuel AN grade 100/130. Engine limits Low impeller ratio 6.46:1 Maximum continuous: (Sea level) 44.0 in.hg., 2400 rpm (2100 hp) (Straight line manifold pressure variation with altitude to 4400 ft.) 42.5 in. hg., 2400 rpm (2100 hp) Take-off (two minutes): (Sea level) 51.5 in.hg., 2800 rpm (2500 hp) (Straight line manifold pressure vari ation with altitude to 3100 ft.) 51.0 in.hg., 2800 rpm (2500 hp). High impeller ratio 8.67:1 Maximum continuous: (9000 ft.) 42.5 in.hg., 2400 rpm (1800 hp) (Straight line manifold pressure vari ation with altitude to 16000 ft.) 41.0 in.hg., 2400 rpm (1800 hp). Take-off (two minutes): (10800 ft.) 44.0 in.hg., 2600 rpm (1900 hp) (Straight line manifold pressure vari ation with altitude to 15700 ft.) 43.5 in.hg., 2600 rpm (1900 hp). Airspeed limits Level fli ght or climb - 271 mph (236 knots) for sea level to 16000 ft. Above 16000 ft. reduce speed 5 mph (4 knots) for each additional 1000 ft. of altitude. Flaps extended (Landing position) 146 mph (127 knots) (Approach position) 146 mph (127 knots) (Take-off position) 200 mph (174 knots) Landing gear extended or during gear operation - 175 mph (152 knots) Glide or dive Without Speedpak and/or deicer boots inst alled - 324 mph* (282 knots) for sea level to 13000 ft. Above 13000 ft. reduce speed 6 mph (5 knots) for each additional 1000 ft. of altitude. (*Note: When airspeed inst rument (0-305 mph) is installed, the above-noted glide or dive speed should read 305 mph instead of 324 mph and the corresponding altitude should read 16000 ft. instead of 13000 ft.) With Speedpak and/or deicer boots installed - 300 mph (261 knots) for sea level to 17000 ft. Above 17000 ft. reduce speed 6 mph (5 knots) for each additional 1000 ft. of altitude. Usable ceilings See Approved Oper ating Manual (enroute climb curve). C.G. range See NOTE 1(b) for require d loading and gear retraction moment. Condition Weight Flap Landing Fwd. Limit Aft. Limit lbs. Position gear sta. %MAC sta. %Mac Take-off 98,000 Takeo ff Down 535.6 20.3 556.4 32.0 Climb or cruise 86,500 Ta keoff Down 531.7 18.0 556.4 32.0 or less Straight line variation between above listed values. Climb or cruise 98,000 Up Up 530.6 17.4 559.9 34.0 86,500 Up Up 526.4 15.0 559.9 34.0 or less Straight line variation between above listed values. Landing 89,500 Down Down 531.7 18.0 556.4 32.0 o r l e s s Weight limits Landing: 86,500 lbs. (See NOTE 19 for 89,500 lbs.) Take-off: 98,000 lbs. (Dump valves are required) 3-engine ferrying: 80,000 lbs. See NOTE 11 for other conditions applicable. Minimum crew 3, Pilot and Copilot at +190 and Flight engineer at +226. A-763 10 Passengers Maximum 60 (CAR 4b.3812). See Approved Weight and Balance Report for actual number and location. Baggage See NOTE 4. Fuel capacity Tanks 2 and 3 (inboa rd) (790 gal. ea.) 9,480 lbs. (+563). Tanks 1 and 4 (outboard) (1 ,555 gal. ea.) 18,660 lbs. (+558). See NOTE 5 regarding "System Fuel and Oil". Oil capacity With Item 1(b) propeller - 2 inboard tanks (56 gal. ea.) 840 lbs. (+455) 2 outboard tanks (56 gal. ea.) 840 lbs. (+474). With Item 1(d), propeller - 2 inboard tanks (54 gal. ea.) 810 lbs. (+455). 2 outboard tanks (54 gal. ea.) 810 lbs. (+474). Control surface movements Main surfaces (booster pressure on) - Elevator 40° up 20° down Aileron 25° up 9° down Rudder 30° right 30° left Tabs (main surfaces in neutral) Elevator 22° up 22° down Aileron 12° up 12° down Rudder 25° right 25° left Flaps - 41° total angular travel. With Model 49 flaps installed in accordance with LAC Dwgs. 251010, 251011 and 273326, flap movement is reduced to 41 . Serial Nos. eligible 2501 and up Required equipment 1b, d, e, f or g; 101(b) or (c); 108(b); 200(b); 201(f) or (g); 202(a), (b), (c) or (d); 203(b) or (e); 205(b), (c) or (d); 206(c) or (d); 209; 508; 600; 601. Specifications Pertinent to All Models Datum 601.5 inches forward of stub wing jack points. MAC 176 inches. Leading edge of MAC - station 500. Leveling means Leveling points on left side of fuselage at stations 230 and 747. Certification basis Type Certificate No. 763. See NOTE 14 regarding applicable regulations. Compliance with the ditching provisi ons of CAR 4b.292(4b.261) has been shown. Production basis Production Certificate No. 600. Export eligibility Eligible for export to all countri es, subject to the provisions of ASR 312 (MOP 2-4 contains the same information) except as follows: Canada: Landplane -eligible Skiplane - not eligible Equipment: A plus (+) or minus (-) sign preceding the weight of an optional item indicates the net weight change when that item is installed. Approval for the installation of all items of equipm ent listed herein has been obtained by the aircraft manufacturer except those items preceded by an asterisk (*). The asterisk denotes that approval has been obtained by someone other than the aircraft manufactur er. An item marked with an asterisk may not have been manufactured under a CAA monitored or approved quality control system, and therefore attention should be paid to workmanship and conformity w ith pertinent data called for in this specification. Propellers and Propeller Accessories (Except De-icing Equipment) 1a. (1) 4 Propellers - Ham. Std. hubs 33E60, blades 6801-0 2,044 lb. (+396) Diameter: Max. 15' 1-1/8", mi n. allowable for repairs 14' 9-1/4". No further reduction permitted. Low pitch setting 15° (17° optional) at 72 in. sta., propeller feathering pitch setting must prevent engine windmilling (approx. 82°) (Eligible with 745C18BA-3 engines). 11 A-763 (2) (a) 4 Feathering Pumps Ha m. Std. 59664-11 or 44 lb. (+464) (b) 4 Feathering Pumps Pesco 1E521DC or 1E521-JC or44 lb. (+464) (c) 4 Feathering Pumps Pesco 1E-777-BAC-1 44 lb. (+464) (3) (a) 4 Governors Ham. Std. 3G8A33G1 or 44 lb. (+415) (b) 4 Governors Ham. Std. 3G8B33G1 or 44 lb. (+415) (c) 4 Governors Ham. Std. 3G8C36M or 44 lb. (+415) (d) 4 Governors Ham. Std. 5G8A36M 36 lb. (+415) b. (1) 4 Propellers - Curtiss Wright hubs C632S-A or C632S-B, 1,668 lb. (+380) blades 850-4C2-0 Diameter 15'1". Pitch settings at 54 in. sta.: low forward +22°, low reverse - 21°, propeller feathering pitch setting must prevent engine windmilling (approximately 89°). (Eligible only with 749C18BD-1 engines and at 102,000 pounds maximum gross weight). When this propeller is installed the following placard shall be placed at two locations: (1) in full view of both pilots and (2) in full view of the flight engineer: "In flight avoid continuous operation below 1625 rpm and between 1725 to 1850 rpm, 1900 to 2000 rpm and 2050 to 2375 rpm. On ground avoid continuous operation between 1200 to 1500 rpm." In addition to the above placard the tachometers shall be marked as follows: Red band 1200 to 1625 rpm. Green band 1625 to 1725 with green radial line at 1675 rpm. Red band 1725 to 1850 rpm with green radial line at 1875 rpm. Red band 1900 to 2000 rpm. Green band 2000 to 2050 rpm with green radial line at 2025 rpm. Red band 2050 to 2375 rpm with green radial line at 2400 rpm. Yellow band 2400 to 2800 rpm at red radial line at 2800 rpm. (2) 1 Synchronizer Master Unit - Curtiss 119778-20 39 lb. (+195) (3) 4 Alternators - Curtiss 102750-2 15 lb. (+390) (4) 2 voltage Boosters-Bendix 1544 Model 2 Curtiss 116285-231 40 lb. (+253) (5) 1 Master Unit Filter - Curtiss 112148-9 6 lb. (+171) (6) 4 Nacelle Filters - Curtiss 111872 10 lb. (+461) c. Deleted (March 30, 1948). d. (1) 4 Propellers - Ham. Std. hubs 23260, blades 2F17K3-24R or 2F17E3-24R 1,758 lb. (+381) Diameter 15'1". Pitch settings at 72 in. sta.: low forward +14°, low reverse -17°, propeller feat hering setting must prevent engine windmilling (approximately 84°). Avoid continuous operation below 1400 engine rpm in flight. (For use with 749C18BD-1 engines only.) (2) 4 Synchronizing Governors Ha m. Std. 5U-18-E30AG 54 lb. (+400) (3) (a) 4 Master Synchronizer Genera tors Kollsman 1135GF, 1020304, or 16 lb. (+446) (b) 4 Master Synchronizer Ge nerator Kollsman 1135GF, 1040304 16 lb. (+446) (4) 1 Propeller Synchronizing Contro l Box Ham. Std. Dwg. 320300 40 lb. (+190) (5) 4 Feathering Pumps - Pesco 1E-777-EL-1 54 lb. (+470) e. (1) 4 Propellers - Ham. Std. hubs 33E60, blades 6801-0 or 6853-0 2,044 lb. (+381) Diameter: Max. 15' 1-1/8", min. allowable for repairs 14' 9-1/4". No further reduction permitted. Low pitch settings 15° (17° optional at 72 in. station, propeller feathering pitch setting must preven t engine windmilling (approximately 82°). (Airplanes equipped with 749C18BD-1 engines eligible for 102,000 pounds maximum gross weight with 6853A-0 blades and 107,000 pounds maximum gross weight wh en 6801A-0 blades are installed.) (2) 4 Synchronizing Governors Ha m. Std. 5U-18-E30AG 54 lb. (+400) (3) (a) 4 Master Synchronizer Genera tors Kollsman 1135GF, 1020304, or 16 lb. (+446) (b) 4 Master Synchronizer Gene rators Kollsman 1135GF, 1040304 16 lb. (+446) (4) 1 Propeller Synchronizing Contro l Box Ham. Std. Dwg. 320300 40 lb. (+190) (5) 4 Feathering Pumps Pesco 1E-777-EL-1 54 lb. (+470) A-763 12 f. (1) 4 Propellers-Curtiss Wright hubs C634S-C306 or C634S-C308, 2,661 lb. (+380) blades 830-21C4-0. Diameter 15'0". Pitch settings at 54 in. sta.: low forward 20.3°, low reverse -14.3°, propeller feathering pitch setting must prevent engine windmilling (approximately 89.7° with C634S-C306 hub and 90.5° with C634S-C308 hub). (Eligible with 749C18BD-1 engines only) (2) 1 Synchronizer Master Unit-Curtiss 119778-20 39 lb. (+195) (3) 4 Alternators - Curtiss 102750-2 15 lb. (+390) (4) 2 Voltage Boosters - Bendix 1544 Model 2 Curtiss 116285-231 40 lb. (+253) (5) 1 Master Unit Filter - Curtiss 112148-9 6 lb. (+171) (6) 4 Nacelle Filters - Curtiss 111872 10 lb. (+461) g. (1) 4 Propellers - Ham. Std. hubs 43E60, blades 6869-0 or 6901-0 2,284 lb. (+381) Diameter: Max. 15' 1-5/16", min. allowable for repairs 14' 9-3/16". No further reduction permitted. Pitch settings at 72 in. sta.: low forward 13°, low reverse -20.5°, propeller feathering setting must prevent engine windmilling (Approximately 81.5°). (Elig ible with 749C18BD-1 engines only) (2) 4 Synchronizing Governors - Ham. St d. 5U-18-E34AS or 5U-18-2 52 lb. (+400) (3) 4 Feathering Pumps - Pesco 1E-777-ML-1 58 lb. (+472) (4) 4 Master Synchronizer Gene rators Kollsman 1135 GH0120304 16 lb. (+446) (5) 1 Propeller Synchronizing Contro l Box Ham. Std. Dwg. 320300 40 lb. (+190) Engines and Engine Accessories - Fuel and Oil System 100. Fuel dump valve installation per following Lockheed Drawings: Model 48-46 - Drawings 254009 or LAC Service Bulletins 49/SB-158; Model 649-79 - Drawings 254009, 294076 or 297581; Models 749-79 and 749A-79 - Drawings 292594, 293781 and either 254009 or 294076 or 297581; Model 149-46 - Drawings 292594, 293781 and either LAC Service Bulletin 49/SB-158 or Drawing 254009. See NOTE 3 regardi ng use of dump valves. 101. System fuel and oil (See NOTE 5 for definition). (a) Model 49-46 685 lb. (+480) (b) Model 649-79 and 649A-79 (with propeller Item 1(b) or (f) installed) 663 lb. (+481) (c) Model 649-79 and 649A-79 (with propeller Item 1(d), (e) or 818 lb. (+470) (g) installed) (d) Models 749-79 and 749A-79 (with propeller Item 1(b) or (f) installed) 718 lb. (+489) (e) Model 749-79 (with propeller Item 1(d), (e) or (g) installed) 873 lb. (+477) (f) Model 149-46 740 lb. (+487) 108. Fuel dump standpipes (See NOTE 9 re garding quantities of undumpable fuel). (a) Model 49-46 (b) Models 649-79, 749-79 and 749A-79 (c) Model 149-46 109. Exhaust System (a) 4 Collectors Solar A169000000 Inconel, or 324 lb. (+434) (b) 4 Collectors Solar 3299 Stainless Steel, or 266 lb. (+434) (c) 4 Sets jet exhaust stacks Rohr P/N 55-5200-1000 Installed in 380 lb. (+433) accordance with Lockheed Service Bulletins 49/SB-600 or 49/SB-600A (Models 649/749 Series) Landing Gear 200. 2 main gear shock struts (a) Cleveland 8298B 948 lbs. (+586) (b) Cleveland 8298C 975 lbs. (+586) (c) Cleveland 8298D 951 lbs. (+586) (d) Cleveland 8298F with either -85 or -85A axle 989 lbs. (+586) (e) Cleveland 8298G 1000 lbs. (+586) (f) Cleveland 8298BA 948 lbs. (+586) (g) Cleveland 8298DA 951 lbs. (+586) (h) Cleveland 8298GA 1000 lbs. (+586) 13 A-763 201. Nose gear shock strut See NOTE 15 regarding struts eligible on Model 149 (a) Cleveland 8297B 463 lbs. (+195) (b) Cleveland 8297C 463 lbs. (+195) (c) Cleveland 8297D 463 lbs. (+195) (d) Cleveland 8297E 463 lbs. (+195) (e) Cleveland 8297F 463 lbs. (+195) (f) Cleveland 8297G 463 lbs. (+195) (g) Cleveland 8297H 463 lbs. (+195) 202. 4 main wheel-brake a ssemblies, 17.00-20, Type III (a) Goodyear Model 20DHBM 887 lbs. (+579) Wheel Assembly No. 530402-M (See AD note 48-1-1) Brake Assembly No. 511031-M (b) Bendix Type B 732 lbs. (+579) Wheel Assembly No. 145340M Brake Assembly No. 145570, 145570M-C or 145570M-CR Use of only Bendix 145340 M/M-1 wheels stamped "MSL 25000, 26000 or 26750" is approved. These wheels are serial 6A1426 and up. (c) Bendix Type B 766 lbs. (+579) Wheel Assembly No. 145340M Brake Assembly No. 145570M-CR2 or 146892M-ST Use of only Bendix 145340 M/M-1 wheels stamped "MSL 25000, 26000 or 26750" is approved. These wheels are serial 6A1426 and up. Bendix Brake Assemblies 145570M-C and 145570M-CR may be reworked as described in Lockheed Service Bulletin 49/SB-545 and reidentified as Bendix Brake Assembly No. 145570M-CR2 (Identical to 146892M-ST). (See NOTE 14). (d) Bendix Type B-3 804 lbs. (+579) Wheel Serial 19A3497 and up 836 lbs. (+579) Wheel Assembly No. 146884M-1 Brake Assembly No. 146892M-ST or 145570M-CR2 (e) Goodrich Model 1752M (This installa tion requires replacement 820 lbs. (+582) of the two Bendix 7 1/2" accu mulators with two Vickers 10" accumulators P/N AA-14009B) *(f) Goodrich Model 1754M Wheel Assembly No. H-3-735 772 lbs. (+579) Brake Assembly No. G-2-597 248 lbs. (+579) (Per TWA Engineering Order 5144A & Capial EP 24) *(g) Bendix Type B-4 Wheel Assembly No. 146884A-1 572 lbs. (+579) Brake Assembly No. 147772A-STR 446 lbs. (+579) or Brake Assembly No. 147772M-STR 424 lbs. (+579) *(h) Goodyear Model L20HBA or LF20HBM Wheel Assembly No. 9540433 492 lbs. (+579) or Wheel Assembly No. 9540552 512 lbs. (+579) or Wheel Assembly No. 9540753 542 lbs. (+579) or Wheel Assembly No. 9540832 546 lbs. (+579) or Wheel Assembly No. 9540891 526 lbs. (+579) Brake Assembly No. 9540534 428 lbs. (+579) (Per TWA Engineering Order 5090B) 203. 4 main wheel tires, 17.00-20, Type III, with tubes: Total permissible wt. 860 lbs. (+582) (b) 16-ply rating (e) 20-ply rating 205. 2 Nose wheel assemblies (1) 33 in., Type I (a) Bendix Type B-3, Assembly No. 57608PA 64 lbs. (+184) (b) Bendix Type B-5, Assembly No. 57608M 54 lbs. (+184) (2) 34x9.9, Type VII B (c) Bendix Type B-1, Assembly No. 146066M 69 lbs. (+184) (d) Goodrich Model 6250M, Assembly No. H-3-592-M 67 lbs. (+184) A-763 14 206. 2 nose wheel tires with tubes; Total permissible wt. 124 lbs. (+184) (c) 10-ply rating, 34x9.9, Type VII B, Plain or Goodrich Rotovane (d) 10-ply rating, 33 in., Type I 209. 2 main gear drag strut dampers, LAC Dwg. 299282 246 lbs. (+572) Electrical Equipment (See Approved Weight and Balance Report for each aircraft.) Interior Equipment 400. Surface Control Equipment a. Automatic pilot (1) Sperry A-3 (3 servos C6-S1-C) (LAC Models 49 & 149 only) 93 lbs. (+160) (2) Pioneer PB-10 (3 servos 15601-1A, 1 servo 15620-2A) 233 lbs. (+624) Servo stall forces measured at pilot's controls: Elevator 25 lbs. + 5 Aileron 25 lbs. + 6 Rudder 90 lbs. + 30 (These forces have not been de monstrated for Flight Path Control) Terrain clearance minimum is 500 feet in cruise configurations, and is 200 feet in approach with pilot's seat belt fastened and hand on control wheel. 420. 2 cabin superchargers (a) LAC part No. 644155, B change (Models 49-46 and 149-46) 115 lbs. (+511) (b) Airesearch Type 52077-50 (Models 649-79, 649A-79, 302 lbs. (+513) 749-79 and 749A-79), Dry (c) Stratos Type S60-1 (Models 649, 749 a nd 749A) installed in accordance 262 lbs. (+509) with Stratos Corporation Dwgs. Nos. 14675B and 14676B (d) Airesearch Type 52077-70, Dry 302 lbs. (+513) (e) Airesearch Type 52077-80, Dry 322 lbs. (+513) (f) Stratos Type S60-5 (Model 49-46 and 149-46 only) when installed in 262 lbs. (+509) accordance with Pan American World Airways data, Miami, Fla. 421. 2 cabin supercharger driveshafts (a) LAC part No. 644280, B change, with guards 64 lbs. (+481) (Models 49-46 and 149-46) (c) LAC part No. 644280-500 including gua rds and Stratos 15,000 70 lbs. (+481) disconnect installation (Models 49-46 and 149-46) (d) Airesearch Type 55040-50, with guards 105 lbs. (+478) (Models 649-79, 749-79 and 749A-79) (e) Airesearch Type 56240 shaft with LAC 305199 Disconnect 107 lbs. (+478) 424. Cabin refrigerating unit installation (a) Refrigerating unit (1) Airesearch Type 52068 (Serial 7-600 and up) 155 lbs. (+613) (2) Airesearch Type 52068-60, -70 146 lbs. (+613) (b) One temperature control installation Dwg. No. 299305 8 lbs. (+590) (Not required with 52068-70 or subsequent refrigerating unit) (c) Two supercharger relief valves Dwg. No. 299257 4 lbs. (+615) (d) One water separator, Aire search Type 1967SG 22 lbs. (+675) Deicing Equipment 500. Wing deicer boots and attachments - G oodrich Model 310 (Use of 157 lbs. (+516) deicer boots between fuselage and inboard nacelle is optional). 501. Stabilizer deicer boots and attach ments - Goodrich Model 310 55 lbs. (+1119) 502. Fin deicer boots and attachment s - Goodrich Model 310 28 lbs. (+1152) 508. Windshield wipers: either (a) One dual Marquette Type 22V5E (Electric) or 12 lbs. (+189) (b) One dual Marquette Type 22V24E (Electric) or 12 lbs. (+189) (c) Two Marquette Type 50V51 (Hydraulic) 7 lbs. (+173) 15 A-763 Miscellaneous (not listed above) 600. CAA Approved Operating Manual (Airplan e Flight Manual) including Section IV, ICAO Requirements, for Models 749 and 749A. (A manual containing information required for the Airplane Flight Manual may be carried in lieu thereof in aircraft operated under the provisions of Parts 40, 41 and 42 of the Civil Air Regulations.) 601. Emergency ladder 607. Speedpak external cargo carrier. (Airplane must be operated in accordance with Appendix I to the CAA Approved Operating Manual.) S ee NOTE 8 for loading and capacities of Speedpak. NOTE 1. (a) Current weight and balance report including list of equipment included in certificated weight empty, and loading instructions, must be in each aircraft at the time of original certification and at all times thereafter (except in the case of air carrier operators having an approved weight control system). See approved Master Equipment List (LAC Report 6056) for list of approved ite ms of equipment in addition to those items listed in this specification. (b) The airplane must be loaded so that the C.G. is within the specified limits at all times, with the effects of fuel use, gear retraction, and movement of crew and passengers from their assigned positions being considered (retraction of the main and nose gears causes the C.G. to move forward, the change in moment due to this retraction being 139,000 in. lb. for landing gears with wheel Item 202(a), 124,000 in.lb. for wheel Item 202(b), and 128,000 in.lb. for wheels Item 202(d) and tir es Item 203(e). Add 3,000 in.lb. to each of the above moments when drag strut dampers are installed.) At take-off, the airplane shall be loaded so that, due to fuel use, the C.G. cannot move forward of 18% MAC unless it can be shown that the C.G. can be easily and rapidly shifted in flight (see CAR 4.70) to meet the 18% forward landing limit. The load manifest form shall indicate the exact load shifting necessary duri ng flight. A 34% aft C.G. limit (gear retracted) for cruising flight may be used when the effect of passenger and crew movements from their assigned positions has been taken into account. For Model 49-46 only, see Notes in Approved Operating Manual concerning trim speeds necessary to permit use of 34% aft C.G. limit and concerning operations with take-off C.G. aft of 29% MAC. NOTE 2. The following placards shall be installed so as to be in full view of the pilots or flight engineer: (a) The following airplane placards for fuel distribution shall be installed: "This airplane must be fueled and the fuel used in accordance with the chart contained in the Approved Operating Manual." "At all times fuel in tanks 2 and 3 must not exceed fuel in tanks 1 and 4, respectively." "Fuel transfer from one tank to another is not permitte d. When operating the fuel system on crossfeed, the tank not being used must be turned off." (b) "This airplane shall be operated in accordance with Part I (Operating Limitations) of the CAA Approved Operating Manual" (all models). (c) "Above 16,000 ft. altitude, the maximum level flight or climb speed shall be reduced 5 mph for each additional 1,000 ft. of altitude. Above 13,000 ft. altitude , the maximum glide or dive speed shall be reduced 6 mph for each additional 1,000 ft. of altitude," or equivalent. (d) "With de-icer boots installed, the maximum glide or dive speed is 300 mph between sea level and 17,000 ft. altitude. Above 17,000 ft., reduce this maximum speed by 6 mph for each additional 1,000 ft. of altitude," or equivalent. (e) "Do not dump fuel with gear or flaps down or above 218 mph. After dumping fuel, move lever to the red line first, then back to intermediate position for 15- 30 seconds before closing." (To be placed adjacent to dumping controls for fuel ta nks Nos. 1, 2, 3, and 4.) (f) Unless "Fasten Seat Belt" and "No Smoking" signs are installed in the forward passenger compartment, one or more crew members shall be instructed to advise the passengers in this compartment when smoking is not permitted or seat belts must be fastened. The following placards shall be installed in the cabin: (g) Placards restricting use during take-off and landing (except by seats equipped with approved safety belt installations for use of cabin attendants only) and limiting the number of occupants at any time, as follows: Models 49 and 149 men's lounge 3 persons Models 49 and 149 ladies' lounge 3 persons NOTE: No placard required in the -59 interior mens' and ladies' lounges. Models 649, 649A, 749 and 749A men's lounge: -12, -31, -34, -51, -52 interiors 3 persons -21, -22, -32, -33, -35, -44, -46, -50 interiors 4 persons A-763 16 Models 649, 649A, 749 and 749A ladies' lounge: -12 interior 2 persons -21, -22, -32, -35 interior 6 persons -31, -34, -51, -52 interiors 3 persons -33, -44, -46, -50 interiors 4 persons Models 649, 649A, 749 and 749A Fwd. urinal: -31 and -34 interiors 1 person (h) A placard to indicate the maximum capacity of th e replacement seat (for Models 49- 46 and 149-46) at cabin attendants' position, if seat other than described by Lockheed Drawing 290262 is installed. (i) At stewardess' seat location adjacent to main cabin door of Models 649, 649A, 749 and 749A: "Not to be occupied during take-off and landing." (j) "Navigator's stool not to be occupied duri ng take-off and landing unless equipped with an approved safety belt installation." NOTE 3. A. Item 100 must be installed for operation of the ai rplane at weights in excess of maximum landing weight. If provisions other than Item 100 are made for dumping fu el, these fuel dump valves shall be made positively inoperative. B. If Item 10C is installed, the aircraft operation record shall include one of the following statements: (1) Non-Air Carrier : "Fuel shall not be dumped with flaps extended." (2) Air Carrier : (a) With authorized weight in excess of maximu m landing weight - "Landing shall not be made at a weight in excess of maximum landing weight except in accordance with CAR 61.7811. Fuel shall not be dumped except in accordance with CAR 61.7811 and with flaps retracted, and then only if the pilot deems it safer than landing at a weight in excess of maximum landing weight." (b) With authorized weight not in excess of maximum landing weight - "Fuel shall not be dumped except in accordance with CA R 61.7811 and with flaps retracted." NOTE 4. Maximum capacity of internal baggage and st orage compartments (see NOTE 8 for Speedpak data): Vol. Max. Floor Cap. Compt. (cu. ft.) Loading psf (lbs.) C.G. Models 49-46 and 149-46: Fwd. cargo compt., fwd. portion (a) 85 30 or 70 1,100 or 2,500 (+395) Fwd. cargo compt., aft portion (a) 95 30 or 70 1,220 or 2,800 (+475) Aft cargo compt., fwd. portion (a) 143 30 or 70 1,900 or 4,350 (+685) Aft cargo compt., aft portion (a) 122 30 or 70 1,630 or 3,750 (+820) AOA cabin compt., "A" (per LAC/dwg. 291835) 45(b) 1,550 (+385) AOA cabin compt., "B" (per LAC/dwg. 291835) 45(b) 2,200 (+436) Coats and luggage 400 (+895) Wash water 350 (+377) Galley installation and supplies (all interiors) 45(b) Models 649-79, 649A-79, 749-79 and 749A-79: Fwd. cargo compt. 154 70 4,900 (+434) Aft cargo compt., fwd. portion 165 70 4,300 (+679) Aft cargo compt., aft portion 115 70 4,300 (+830) Coats and luggage: -21, -22, -32, -35 interiors 500 (+940) -12 interior Left hand fwd. 400 (+273) Right hand fwd. 825 (+376) Left hand aft 150 (+944) -33, -46, -50 interiors 465 (+900) -31, -34 interior 550 (+900) -44 interior Left hand 150 (+900) Right hand 700 (+873) Wash water, -21, -22, -32, -35 interiors 267 (+412) Wash water, -12, -31, -33, -34, - 44, -46, -50, -51, -52 350 (+769) Galley water, -21, -22, -32, -35 interiors 142 (+380) Galley installation and supplies (all interiors) 45(b) 17 A-763 (a) For Models 49-46 and 149-46, cargo compartments are satisfactory for heavier loading, as indicated, when flooring is modified in accordance with Lockheed drawing 293877. This modification was accomplished at the factory on airplane serials 2051 and up. (b) Galley areas between Stations 260 and 451 are structura lly satisfactory for a uniformly distributed load over the entire area of 45 PSF or a uniformly distributed load of 55 PSF on each side of the 20" aisle or a uniformly distributed load of 420# per linear foot. Galley installations and their contents shall not exceed these loadings. Fixed equipments such as galleys shall be listed on the Approved Equipment List together with pertinent weights and arms. NOTE 5. (a) "System Fuel and Oil" is that amount required to fill both systems and the tanks up to the tank outlets to the engines, when the airplane is in the level attitude. For these models, the only "unusable" fuel is "System fuel." (Ref. CAR 4b.112 and 4b.6104.) "System Fuel and O il" and all hydraulic fluid must be included in the certificated weight empty. (b) Fuel and oil tank capacities do not include any "System Fuel and Oil." NOTE 6. On Models 49-46 and 149-46, the carburetor filtered air c ontrols must be rendered inoperative, both at the flight engineer's station and in the nacelles. The four filters must be retained, however, unless the firewall openings are covered with adequate stainless steel plates. NOTE 7. (a) In order that airplane serials prior to 2045 ma y be eligible for certification at landing weights over 75,000 lbs., and take-off weights above 86,250 lbs., the main la nding gear side struts must be replaced and the wing front spars reinforced in accordan ce with Lockheed Service Instructions Nos. 049/SI-14 and 049/SI-14A. These changes were accomplished by the manufacturer on airplane serials 2045 and up. (b) Model 49-46 is eligible for certification at 93,000 lb . take-off weight when modified in accordance with Lockheed Service Bulletin No. 49/SB-282. This modifi cation includes the addition of external rails to the upper forward portion of the fuselage, modification and reidentification of nose and main landing gear struts and the replacement of nose landing gear wheels and tires. This model is also eligible for certification at 83,000 lbs. landing weight when modified in accordance with Lockheed Service Bulletin 49/SB-425. Prior to certification, the pertinent sections of the Operating Manual should be replaced to correspond to the increased take-off and landing weights. (c) Model 49-46 is eligible for certification at 96,000 lb s. take-off weight and 83,000 lbs. landing weight when modified to incorporate reinforcements of the wi ng and landing gear structures in accordance with LAC Service Bulletin 49/SB-548. (d) Model 49-46, Serial Nos. 1970, 1971, 1974 through 1980 and 2021 through 2088, eligible for certification at 98,000 lbs. take-off weight and 84,500 lbs. landing weight when modified to incorporate reinforcements of the wing and fuselage structure in accord ance with LAC Service Bulletin No. 49/SB-759. NOTE 8. (a) Maximum gross weight of Spee dpak and contents - 10,000 lbs. Use actual gross weight and C.G. for weight and balance calculations. (b) The airplane fuel tank venting and dumping systems must be revised in accordance with Lockheed Service Bulletin 049/5B-201 prior to operation of the airplane with Speedpak installed. (c) Maximum capacity of Speedpak compartments: COMPARTMENT Volume Maximum floor per running Capacity Comp. (Cu.Ft.) loading, psf ft. - lb. (Pounds) C. G. A 72 100 290 1440 404 B 40 100 360 790 459 C 46 100 360 930 459 D 50 100 360 1000 525 E 58 100 360 1160 525 F 69 100 260 1380 613 G 75 100 260 1500 613 (d) When Speedpak is installed, the speed limit placards on the pilot's and copilot's instrument panels shall be replaced with new placards listing the speed restricti ons pertinent to use of Speedpak (LAC part No. 296921 or equivalent). (e) Airplane serials up to and incl uding 2084 must be modified to incorporate a guard over the Speedpak fire extinguisher, heater and smoke detector switches prio r to use of Speedpak (LAC Service Bulletin 49/SB-234 describes this modification). A-763 18 (f) Airplane serials up to and including 2081 must be modified to relocate the CO2 discharge indicator prior to initial installation of Speedpak (LAC Service Bulletin 49/SB-235 describes this modification). (g) Airplane serials up to and including 2075 must be modi fied in accordance with Lockheed Service Instruction 49/SI-8 to permit installation of Speedpak. NOTE 9. Undumpable fuel, as liste d below, must be included in landing weight. (Values listed are usable fuel and do not include any system fuel covered by Item 101): Model Condition Gallons remaining in tanks 2 and 3 1 and 4 2a and 3a* 49 (No standpipes) 20 ea. 65 ea. 49, 149 (With standpipes, per LAC Serv ice Instr. 49/SI-12)** 182 ea. 225 ea. 1 ea. 49, 149 (With standpipes, per LAC Serv ice Bull. 49/SB-403)** 116 ea. 136 ea. 1 ea. 649, 649A** 116 ea. 136 ea. 749, 749A** 116 ea. 136 ea. 1 ea. *Tanks 2a and 3a are installe d in Models 149, 749 and 749A only. **On all models equipped with standpipes, e ither the ram pressure type fuel tank vents or the suction cut-off type vents may be used on tanks 1, 2, 3 and 4. Ram vents must be retained on tanks 2a and 3a of Models 149, 749 and 749A airplanes. NOTE 10. (a) The approved Operating Manual mu st cover at least the following valves: Model Condition Gallons in tanks 2 and 3 1 and 4 2a and 3a* 49 Max. fuel at land. wt. (90,000 lb. rake-off wt.) 790 ea. 900 ea. 49 Max. fuel at land wt. (93,000 lb. and 96,000 lb. 790 ea. 1,555 ea.. take-off wt.) 149, 749 Max fuel at land. - either 790 ea. 1,200 ea. 100 ea. and 749A or 790 ea. 1,200 ea. 0 649, 649A Max. fuel at land. 790 ea.. 1,555 ea. *Tanks 2a and 3a in Models 149, 749 and 749A only. (b) For minimum fuel at any take-off wei ght, refer to fuel loading and usage chart in the pertinent Approved Operating Manual. NOTE 11. Ferry permits may be issued to Mode l 49 Series aircraft on which one engine is inoperative with its propeller removed or feathered under the following conditions: (a) Operation of aircraft shall be in accordance with pe rtinent limitations contained in the applicable portion of the CAA Approved Operating Manual, pertin ent appendicies and existing instructions. (b) (1) Maximum take -off weight 80,000 lbs. (2) Maximum landing wei ght (Model 49-46) 77,800 lbs. (c) C.G. range: See applicable portion of specification above. NOTE 12. Tail bumper installation may be removed in accordance with LAC Service Bulletin No. 49/SB-346. NOTE 13. Aircraft in their original configur ation have the following elevator boost ratios: Models 49-46: 9:1 Model 149-46, 649-79, 749-79 and 749A-79: 15:1 The boost ratio for Models 49-46 may be increased to 15:1 in accordance with LAC Service Bulletin 49/SB-355. 19 A-763 NOTE 14. Interrelationship of various models. Weight in pounds Model 1 Take- Certification design. off Landing basis Remarks 49 3 86,250 75,000 CAR 4a Basic model- conversion of AAF model C-69. (Transport Category 49 2,3 90,000 77,800  See NOTE 7(a) for required modifications for (49A)  these weights.  49 2,3 93,000 77,800  See NOTE 7(b) Basic model modified to (49B)  incorporate forward fuselage reinforcements, different  shock strut metering pins a nd different nose gear wheels  and tires. (Refer LAC 49/SB-282) 49 2 93,000 83,000 Combination See NOTE 7(b). Same as preceding, except (49C) CAR 4b & higher landing weight substantiated in CAR 4a accordance with CAR 4b performance requirements. (Transport (Refer LAC 49/SB-425) Category) 49 2 96,000 83,000  See NOTE 7(c). Same as preceding except for (49D)  higher take-off weight, wing and landing gear  reinforcements per LAC Service Bulletin 49/SB-548. 49 2 98,000 84,500 See NOTE 7(d). Same as preceding except for (49E) higher take-off and landing weights; wing and fuselage reinforcement per LAC Service Bulletin 49/SB-759. 149 2 100,000 83,000  Same as preceding, but with Model 749 outer wing panels.  Different basic fuel distri bution required. Model 149  identical or equivalent structurally to Model 749 except  for inner wing panels. Modi fications described in LAC  Service Bulletin 49/SB-66.  649 2 94,000 84,500  Basic production model. Differs from Model 49  in following major respects: Engines, propellers, cabin  superchargers and driveshaft s, oil tanks, shock strut  metering pins, fuselage and inner wing reinforcements,  and flap deflection. 649A 2 98,000 86,500  Same as preceding except for higher take-off and landing (See NOTE 19)  and landing weights of 98,000 lbs. and 86,500 lb.,  respectively. Incorporates inner wing reinforcements,  new L.G. struts (8298F). These modifications are  covered in LAC SB 49/SB-503 Change A. These  airplanes also eligible for certification as Model 749A  when provisions of LAC Service Bulletin 49/SB-614  are accomplished. 749 2 102,000 84,500 Combination Model 649 with integr al fuel tanks in outer wing panels. (See CAR 4b & NOTE 17) CAR 4a (Transport Category). ICAO DOC Annex 8 (See NOTE 18) 749A 2 107,000 89,500  Model 749 modified to incorpor ate reinforcements of wing  center section, inner wing, a nd fuselage structure between  stas. 527.6 and 603.2; new main L. G. struts (8298F);  20-ply rating main tires; new or revised brakes. These  modifications are covered by LAC S.B. 49/SB-500; -500A  and -545. A-763 20 1Dash numbers indicate engine installation: -46: Wright 745C18BA-3 -79: Wright 749C18BD-1 2Complies with CAR 4b ground loads requirements. 3Structural zero fuel for the Model 49 at 90,000/93,000 lb. take-off and 77,800 lb. landing weights is 75,960 lbs. For all other models, structural adequacy has been shown when the undumpable fuel specified in NOTE 9 is included in the landing weight. (Models shown in parenthesis( ) are the LAC designations for the specified weight category). NOTE 15. (a) Model 49 main gear shock stru ts listed as Equipment Items 200(a) or (c), if modified in accordance with LAC Service Bulletin 49/SB-66, are also eligible for us e on model 149 aircraft. These modified struts are identified as Cleveland Types 8298BA. (b) Model 49 nose gear shock struts, lis ted as Equipment Items 201(a), (b), (c), (d), or (e), if modified in accordance with LAC Service Bulletin 49/SB-66, are al so eligible for use on model 149 aircraft. These modified struts are identified as Clev eland types 8297BA, 8297BC, 8297CA, 8297DA or 8297FA. NOTE 16. (a) Model 749 aircraft are also eligible for certif ication with installation of large cargo door described by LAC Drawing No. 299984. (b) Military Models VC121-B and C-121A are essentia lly identical to model 749 aircraft modified in accordance with (a) above and are eligible for civil certification with the following stipulations: (1) The manufacturer's nameplate on the airplane shoul d be altered to show the date of conversion and the designation "Model 749-79." (2) Life rafts installed in the vicinity of the naviga tor's station must be removed or relocated to eliminate the interference with the em ergency exit in that vicinity. (3) Each airplane should be inspected for possible hidden damage, satisfactory workmanship and materials utilized in making repairs and/or alterations, complia nce with applicable Airworthiness Directive Notes, installation of approved equipment (see NOTE 1), a nd for additions or changes accomplished subsequent to delivery which may adversely affect the operation as a civil aircraft. NOTE 17. The conversion of Model 749 aircraft to Model 749A is covered by LAC Service Bulletins 49/SB-500, -500A and -545. Since production changes similar to the modifications described in Bulletin 49/SB-500 were incorporated in serial Nos. 2589, 2590, 2601 and subsequent prior to their delivery from the factory these aircraft are eligible for certification and Model 749 at ma ximum landing and take-off weights of 86,500 lbs. and 102,000 lbs., respectively. The landing weight may be increased to 89,500 lbs. when provisions of Service Bulletin 49/SB-545 are incorporated. NOTE 18. All Models 749-79 and 749A-79 aircra ft are eligible for certification at maximum takeoff weights of 102,000 lbs. and 107,000 lbs. respectively, in accordance with the ICAO Category "A: Standards set forth in Document Annex 8 dated April, 1949. The Flight Manuals for all airc raft so certificated must be amended to include Section IV, ICAO Requirements. NOTE 19. Model 649A aircraft are eligible for certification at landing weight of 89,500 lbs. when new wheels and brakes are installed in accordance with LAC Service Bulletin 49/SB- 545. When the above change is made the forward C.G. position for the 98,000 lb. maximum take -off weight is revised as follows: Take-off condition Sta. 534.4 (19.5%) Climb or cruise Sta. 529.2 (16.6%) No correction of C.G. position is required fo r the increased landing weight of 89,500 lbs. NOTE 20. The electric drive on the elevator trim tab mechanism on the control pedestal, formerly considered as an integral part of the airplane, may be retained or removed at the option of the operator. NOTE 21. In accordance with the agreement between the Department of Defense and the Civil Aeronautics Board, all air carrier operators utilizing aircraft which have been modi fied under the Civil Reserve Air Fleet Program, Part I, Phase II, may deduct the added weight of military modifi cation up to a maximum of 50 lbs. for each aircraft so modified. -END- ``` ## ADs (97, first 50, in force first) - [AD 2026-13-02](https://openairdocs.org/ad/2026-13-02): Navigation · Airbus Canada Limited Partnership 18, 49-46, 80-A and 555 more. Effective Jul 1, 2026 - [AD 2023-10-02](https://openairdocs.org/ad/2023-10-02): Indicating/Recording System, Navigation · Boeing 18, 23, 35 and 1,060 more. Effective May 26, 2023 - [AD 93-14-12](https://openairdocs.org/ad/93-14-12): Crewmember Protective Breathing Equipment Units · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 201 more. Effective Sep 2, 1993 - [AD 71-07-02](https://openairdocs.org/ad/71-07-02): Obstacle Clearance Profile · Lockheed 1049-54, 1049B-55 (Navy R7V-1), 1049C-55 and 12 more. Effective Apr 3, 1971 - [AD 67-03-05](https://openairdocs.org/ad/67-03-05): Propeller Vibratory Stresses · Lockheed 1049-54, 1049B-55 (Navy R7V-1), 1049C-55 and 9 more. Effective Jan 23, 1967 - [AD 64-13-03](https://openairdocs.org/ad/64-13-03): Nose Landing Gear Rod Ends · Lockheed 1049-54, 1049C-55, 1049D-55 and 9 more. Effective Jun 12, 1964 - [AD 64-07-04](https://openairdocs.org/ad/64-07-04): Flight Control Boost Systems · Lockheed 1049-54, 1049C-55, 1049D-55 and 9 more. Effective Apr 14, 1964 - [AD 64-03-03](https://openairdocs.org/ad/64-03-03): Blades · Boeing DC-6, DC-6A, DC-6B and 26 more. Effective Mar 1, 1964 - [AD 64-02-05](https://openairdocs.org/ad/64-02-05): Openable Window in the Crew Exit · Overhead emergency exit hatch between fuselage station 278.4… (Flying Tiger Line STC SA4-948). Effective Jan 10, 1964 - [AD 63-25-02](https://openairdocs.org/ad/63-25-02): Nose Landing Gear · Lockheed 1049-54, 1049C-55, 1049D-55 and 9 more. Effective Dec 30, 1963 - [AD 62-26-03](https://openairdocs.org/ad/62-26-03): Main Landing Gear Crossheads · Lockheed 1049-54, 149-46, 49-46 and 4 more. Effective Jan 7, 1963 - [AD 62-19-02](https://openairdocs.org/ad/62-19-02): Main Landing Gear Pistons · Lockheed 149-46, 49-46, 649-79 and 3 more. Effective Sep 24, 1962 - [AD 62-01-02](https://openairdocs.org/ad/62-01-02): Main Landing Gear Cylinders · Lockheed 1049-54, 1049B-55 (Navy R7V-1), 1049C-55 and 11 more. Effective Jan 9, 1962 - [AD 61-24-04](https://openairdocs.org/ad/61-24-04): Horizontal Stabilizer Rear Spar · Lockheed 1049-54, 1049B-55 (Navy R7V-1), 1049C-55 and 11 more. Effective Dec 14, 1961 - [AD 61-19-03](https://openairdocs.org/ad/61-19-03): Elevator Bolt Inspection · Lockheed 1049-54, 1049B-55 (Navy R7V-1), 1049C-55 and 11 more. Effective Sep 8, 1961 - [AD 53-05-01](https://openairdocs.org/ad/53-05-01): Propellers Slip Rings · Aero Spacelines 377, 377MG, 377SGT and 6 more - [AD 47-10-02](https://openairdocs.org/ad/47-10-02): Elevator Tab Control Circuit Breaker · Lockheed 49-46 - [AD 47-10-03](https://openairdocs.org/ad/47-10-03): Rudder and Elevator Circuit Breakers · Lockheed 49-46 - [AD 47-10-04](https://openairdocs.org/ad/47-10-04): Engine Autosyn Transmitter Jumpers · Lockheed 49-46 - [AD 47-10-05](https://openairdocs.org/ad/47-10-05): Landing Gear Selector Valve · Lockheed 49-46 - [AD 47-10-06](https://openairdocs.org/ad/47-10-06): Fuel Tank Shutoff Valves · Lockheed 49-46 - [AD 47-10-07](https://openairdocs.org/ad/47-10-07): Landing Gear Restriction Valve · Lockheed 49-46 - [AD 47-10-08](https://openairdocs.org/ad/47-10-08): Elevator Booster Shifter Horn · Lockheed 49-46 - [AD 47-10-09](https://openairdocs.org/ad/47-10-09): Oil Line Cover Plates · Lockheed 49-46 - [AD 47-10-10](https://openairdocs.org/ad/47-10-10): Voltage Regulator Soundproofing · Lockheed 49-46 - [AD 47-10-11](https://openairdocs.org/ad/47-10-11): Fire Detector Replacement · Lockheed 49-46 - [AD 47-10-13](https://openairdocs.org/ad/47-10-13): Fire Resistant Firewall Fittings · Lockheed 49-46 - [AD 47-10-14](https://openairdocs.org/ad/47-10-14): Fuel Pump Flexible Hose · Lockheed 49-46 - [AD 47-10-15](https://openairdocs.org/ad/47-10-15): Recertification of Lockheed 49 · Lockheed 49-46 - [AD 47-10-16](https://openairdocs.org/ad/47-10-16): Conversion of 49-51 to 49-46 · Lockheed 49-46 - [AD 47-10-17](https://openairdocs.org/ad/47-10-17): Cabin Supercharger Rework · Lockheed 49-46 - [AD 47-10-18](https://openairdocs.org/ad/47-10-18): Fire Resistant Fuel Line · Lockheed 49-46 - [AD 47-10-19](https://openairdocs.org/ad/47-10-19): Cabin Heater Fuel Solenoid Valve · Lockheed 49-46 - [AD 47-10-20](https://openairdocs.org/ad/47-10-20): Alcohol Tank Replacement · Lockheed 49-46 - [AD 47-10-21](https://openairdocs.org/ad/47-10-21): Landing Gear Torque Links · Lockheed 49-46 - [AD 47-10-22](https://openairdocs.org/ad/47-10-22): Fire Extinguisher Valve Washer · Lockheed 49-46 - [AD 47-10-23](https://openairdocs.org/ad/47-10-23): Bathtub Fitting Steel Nuts · Lockheed 49-46 - [AD 47-10-24](https://openairdocs.org/ad/47-10-24): Cross-Feed Relief Valve · Lockheed 49-46 - [AD 47-10-25](https://openairdocs.org/ad/47-10-25): Generator Mounting Bolts · Lockheed 49-46 - [AD 47-10-26](https://openairdocs.org/ad/47-10-26): Flap drain Line Rerouting · Lockheed 49-46 - [AD 47-10-27](https://openairdocs.org/ad/47-10-27): Fuel Tank Vent Outlets · Lockheed 49-46 - [AD 47-10-28](https://openairdocs.org/ad/47-10-28): Elevator Cable Seal Holes · Lockheed 49-46 - [AD 47-10-29](https://openairdocs.org/ad/47-10-29): Aileron Drain Holes · Lockheed 49-46 - [AD 47-10-30](https://openairdocs.org/ad/47-10-30): Fuel Tank Surge Box Flapper Valves · Lockheed 49-46 - [AD 47-10-31](https://openairdocs.org/ad/47-10-31): Landing Gear Torque Arm · Lockheed 49-46 - [AD 47-10-32](https://openairdocs.org/ad/47-10-32): Upper Wing Surface Inspection · Lockheed 49-46 - [AD 47-10-33](https://openairdocs.org/ad/47-10-33): Cylinder Barrel Replacement · Lockheed 49-46 - [AD 47-10-34](https://openairdocs.org/ad/47-10-34): Exhaust System Ball Joint Rework · Lockheed 49-46 - [AD 47-10-36](https://openairdocs.org/ad/47-10-36): Wing Leading Edge Rework · Lockheed 49-46 - [AD 47-10-37](https://openairdocs.org/ad/47-10-37): Landing Gear Fulcrum Bolts · Lockheed 49-46 All 97: https://openairdocs.org/tcds/A-763/ads.md ## Registered aircraft by registry model (OpenAirDocs) - [Lockheed 49-46](https://openairdocs.org/model/lockheed-49-46): 1 aircraft (registry code 5261702) - [Lockheed 749-79](https://openairdocs.org/model/lockheed-749-79): 1 aircraft (registry code 5262002) - [Lockheed 149-46](https://openairdocs.org/model/lockheed-149-46): 0 aircraft (registry code 5261802) - [Lockheed 649-79](https://openairdocs.org/model/lockheed-649-79): 0 aircraft (registry code 5261902) - [Lockheed 649A-79](https://openairdocs.org/model/lockheed-649a-79): 0 aircraft (registry code 5261904) - [Lockheed 749A-79](https://openairdocs.org/model/lockheed-749a-79): 0 aircraft (registry code 5262008) ## STCs approved under this data sheet (31) - [STC ST12461IB](https://openairdocs.org/stc/ST12461IB): Installation of Cockpit Voice Recorder with optional RIPS Upgrade. Mid- Canada Mod Center - [STC SA01967WI](https://openairdocs.org/stc/SA01967WI): Use of GAMI G100UL High Octane Unleaded Avgas. General Aviation Modifications Inc. - [STC SA1-605](https://openairdocs.org/stc/SA1-605): 2015 Series radomes.. Saint-Gobain Performance Plastics Corp - [STC SA24SO](https://openairdocs.org/stc/SA24SO): Cargo loading door in forward section of main cabin and rework of main cabin floor structure.. Anson Robert E & Callaway L C Jr - [STC SA1360WE](https://openairdocs.org/stc/SA1360WE): Installation of Collins Model642C-1 cockpit voice recorder system.. McCulloch Properties Inc - [STC SA1-547](https://openairdocs.org/stc/SA1-547): Modification of floor and support structure for cargo loading.. Flight Enterprises Intl Aircraft Svcs Inc. - [STC SA1-578](https://openairdocs.org/stc/SA1-578): Cabin smoke detector system for cargo operation.. Flight Enterprises Intl Aircraft Svcs Inc. - [STC SA112WE](https://openairdocs.org/stc/SA112WE): Structural mounts in McMillan radome and in cockpit for WP-103 Collins all weather radar.. California Airmotive Corporation - [STC SA1296WE](https://openairdocs.org/stc/SA1296WE): Seats at emergency exit incorporating a free folding back.. McCulloch Properties Inc - [STC SA1319WE](https://openairdocs.org/stc/SA1319WE): Installation of Collins ATC transponder Model 621A-2 with antenna type 237Z-1.. McCulloch Properties Inc - [STC SA3-203](https://openairdocs.org/stc/SA3-203): Smoke detection for cargo compartment.. Trans World Airlines Inc - [STC SA326WE](https://openairdocs.org/stc/SA326WE): Emergency safety equipment.. AiResearch Aivation Service Co - [STC SA327WE](https://openairdocs.org/stc/SA327WE): Cargo tie-down rings for retaining a 4,700 pound R 3350 QEC package.. AiResearch Aivation Service Co - [STC SA354WE](https://openairdocs.org/stc/SA354WE): Observer's jump seat.. California Airmotive Corporation - [STC SA3SO](https://openairdocs.org/stc/SA3SO): Radome and radar provisions for up to 22-inch diameter antenna RCA AVQ-10 or Bendix RDR-1(X/C Band).. Tempo Design Corp - [STC SA4-1500](https://openairdocs.org/stc/SA4-1500): Interior modification for 98 passengers, maximum occupants including crew.. Great Lakes Airlines Inc - [STC SA4-1616](https://openairdocs.org/stc/SA4-1616): Nose radome.. Las Vegas Hacienda Inc - [STC SA4-1634](https://openairdocs.org/stc/SA4-1634): Modification of interior to 81 through 85 and 90 passenger configurations.. California Airmotive Corporation - [STC SA4-1657](https://openairdocs.org/stc/SA4-1657): Structural mounts in McMillan radome and in cockpit for WP-103 Collins all weather radar.. California Airmotive Corporation - [STC SA4-27](https://openairdocs.org/stc/SA4-27): Stratus supercharger and air cycler.. Braniff Airways Inc - [STC SA464CE](https://openairdocs.org/stc/SA464CE): Fairchild Model A-100 cockpit voice recorder.. Trans World Airlines Inc - [STC SA546WE](https://openairdocs.org/stc/SA546WE): Modification of crew entrance door window mechanism.. Gamco Precision - [STC SA642WE](https://openairdocs.org/stc/SA642WE): Operation with mixed Hamilton Standard 43E60/6901 and43E60/6903 propellers.. California Airmotive Corporation - [STC SA66WE](https://openairdocs.org/stc/SA66WE): Oversize cargo door on left side of fuselage aft of wing.. Lockheed Aircraft Service Co - [STC SA776WE](https://openairdocs.org/stc/SA776WE): Collins DME in aircraft.. Edde Airlines Inc - [STC SA83SO](https://openairdocs.org/stc/SA83SO): Oil separator B-300-1.. Air Carrier Eng Service Inc - [STC SA845WE](https://openairdocs.org/stc/SA845WE): Military D-2 auxiliary power unit in Zone 3 of No. 1 nacelle.. Las Vegas Hacienda Inc - [STC SA1-145](https://openairdocs.org/stc/SA1-145): Cabin interior modification for74 to 80 seats, inclusive of galley and crew bunk area.. Flight Enterprises Intl Aircraft Svcs Inc. - [STC SA1-146](https://openairdocs.org/stc/SA1-146): Radio equipment.. Flight Enterprises Intl Aircraft Svcs Inc. - [STC SA1-147](https://openairdocs.org/stc/SA1-147): Goodyear brake assembly 9540534 wheel assembly 9540753, and modification of brake control valve.. Flight Enterprises Intl Aircraft Svcs Inc. - [STC SA1-480](https://openairdocs.org/stc/SA1-480): Smoke detector system in cargo compartments Class B.. Flight Enterprises Intl Aircraft Svcs Inc. --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.